CN106812789A - It is hinged wing self-lubricating thrust bearing - Google Patents

It is hinged wing self-lubricating thrust bearing Download PDF

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Publication number
CN106812789A
CN106812789A CN201611080311.9A CN201611080311A CN106812789A CN 106812789 A CN106812789 A CN 106812789A CN 201611080311 A CN201611080311 A CN 201611080311A CN 106812789 A CN106812789 A CN 106812789A
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CN
China
Prior art keywords
bearing
interior section
section
bearing part
external member
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201611080311.9A
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Chinese (zh)
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CN106812789B (en
Inventor
安迪·泰勒
赖安·皮斯利
迈克尔·赫力格曼
大卫·库姆
马赛厄斯·丁纳
菲利普·查米特
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Roller Bearing Company of America Inc
Original Assignee
Roller Bearing Company of America Inc
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Publication of CN106812789A publication Critical patent/CN106812789A/en
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Publication of CN106812789B publication Critical patent/CN106812789B/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F16C17/08—Sliding-contact bearings for exclusively rotary movement for axial load only for supporting the end face of a shaft or other member, e.g. footstep bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C25/00—Bearings for exclusively rotary movement adjustable for wear or play
    • F16C25/02—Sliding-contact bearings
    • F16C25/04—Sliding-contact bearings self-adjusting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
    • F16C27/06—Elastic or yielding bearings or bearing supports, for exclusively rotary movement by means of parts of rubber or like materials
    • F16C27/063—Sliding contact bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/22—Sliding surface consisting mainly of rubber or synthetic rubber
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/10—Sliding-contact bearings for exclusively rotary movement for both radial and axial load
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2202/00—Solid materials defined by their properties
    • F16C2202/50—Lubricating properties
    • F16C2202/52—Graphite
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2208/00—Plastics; Synthetic resins, e.g. rubbers
    • F16C2208/10—Elastomers; Rubbers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2208/00—Plastics; Synthetic resins, e.g. rubbers
    • F16C2208/20—Thermoplastic resins
    • F16C2208/30—Fluoropolymers
    • F16C2208/32—Polytetrafluorethylene [PTFE]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2208/00—Plastics; Synthetic resins, e.g. rubbers
    • F16C2208/20—Thermoplastic resins
    • F16C2208/70—Polyesters, e.g. polyethylene-terephthlate [PET], polybutylene-terephthlate [PBT]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2229/00—Setting preload
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2326/00—Articles relating to transporting
    • F16C2326/43—Aeroplanes; Helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/20—Sliding surface consisting mainly of plastics
    • F16C33/201—Composition of the plastic

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Support Of The Bearing (AREA)
  • Sliding-Contact Bearings (AREA)

Abstract

The present invention relates to be hinged wing self-lubricating thrust bearing, the bearing includes external member and internals, and the external member has concave inside surface, and the internals has the first and second interior sections.Each in first and second interior section is respectively provided with bottom, and the bottom has the bearing portions for extending from.The bearing portions is collectively forming the convex external surface complementary with the concave inside surface shape.The preloading component engaged with its part is provided between the bearing.Lubricating bushings are provided between the concave inside surface and convex external surface.The bearing portions is located in the external member, to compress the preloading component, so as to the axial movement between the outwardly and inwardly component is limited into a default size.Preloading component outcurve with the abrasion of the bushing, so as to the axial movement is held in into the default size.

Description

It is hinged wing self-lubricating thrust bearing
Cross-Reference to Related Applications
This application claims the U.S. Provisional Patent Application 62/260,794 submitted on November 30th, 2015 and in The rights and interests of the U.S. Provisional Patent Application 62/287,190 that on January 26th, 2016 submits to, the content of two application is by quoting It is fully incorporated herein.
Technical field
Wing thrust bearing is hinged the present invention relates to one kind, more particularly to it is a kind of with lubrication neck bush and preloading component Thrust bearing, the preloading component be used for the axial movement in the bearing is held in pre- limiting before and after the liner wear In degree.
Background technology
In aerospace industry, fuselage manufacturer is being sought the maximizing fuel efficiency and cost minimization of various aircraft The method and apparatus for changing (increasing economic efficiency).In Aero-Space design, manufacturer generally seeks the one side of optimization It is the design of wing.For fixed wing aircraft, wing is more long, and the airplane ascensional force for being obtained is bigger, so as to can improve fuel disappear Consumption efficiency.However, due to the limitation of airport aircraft gate, wing length has limitation.For example, existing airport design is for the aircraft wing Exhibition has limitation.Airport design with international civil aviation (International Civil Aviation Organization, ICAO) code A to F is defined, and its size to the span and undercarriage width and length is limited.In order to overcome this point, Craft wing design is that its part or wing tip backward or can be swung up, to stop in aircraft gate.This is commonly referred to " dioptric type " Design, or band is hinged the aircraft of tilting wing tip.Such as (as shown in Figure 1), when aircraft 100 is stopped at seat in the plane, its alar part or Wing tip 103,103 ' is put from after operating position or upper pendulum is to seat in the plane stop position, wherein, alar part or the self-retaining of wing tip 103,103 ' It is pivoted up in the bottom 102 of airframe 101.After leaving seat in the plane, the alar part or wing tip 103,103 ' are forward or to the bottom It is dynamic, with permission to take off, flight and landing.After landing, the alar part or wing tip 103,103 ' before seat in the plane is reached again backward or It is swung up.
As is further illustrated in figure 1, it is being hinged in tilting wing tip aircraft (being such as hinged tilting wing tip aircraft 100), is using The actuator (not shown) connected with the articulated elements 104 between wing tip 103,103 ' and wing bottom 102.Such articulated elements 104 Promote the relative motion between wing tip 103,103 ' and wing bottom 102 using various bearings (such as thrust bearing).However, thrust Bearing is susceptible to excessively axial movement of wearing and tearing and cause in use, so that wing tip 103,103 ' and wing bottom Mismatch problems are produced between 102.
Therefore, for tilting wing tip aircraft articulated elements, there is a kind of new-type axle for hardly having axial movement The demand held, the demand is to be resolved.
The content of the invention
A kind of bearing for being hinged tilting airplane wingtip articulated elements is disclosed herein.The bearing includes external member, and this is outer Portion's component has the interior zone defined by concave inside surface.The bearing also includes internals, and the internals has the One interior section and the second interior section.First interior section has the first bottom and axially extending from first bottom Clutch shaft bearing part.Second interior section has the second bottom and from the axially extending second bearing portion in second bottom Point.The clutch shaft bearing part and the second bearing part are collectively forming outside the convex complementary with the concave inside surface shape Surface.Preloading component (such as turn or elastic material are provided between the clutch shaft bearing part and the second bearing part Material), the preloading component is engaged with least a portion of the clutch shaft bearing part and/or the second bearing part.It is described Lubricating bushings are provided between concave inside surface and the convex external surface.The clutch shaft bearing part and the second bearing portion At least a portion divided is located in the interior zone so that the preloading component is inside on radially and/or axially direction Compression, so as to outer inclined on radially and/or axially direction, by the axial direction fortune between the external member and the internals It is dynamic to be limited to a default size.The preloading component is suitable to outer on radially and/or axially direction with the abrasion of the bushing Song, the default size is held in by the axial movement.
In one embodiment, the external member includes the first exterior section and the second outside portion that interfix Point.
In one embodiment, first interior section and second interior section interfix.
In one embodiment, the external member is formed with the mounting flange for radially extending.
In one embodiment, the mounting flange includes multiple through holes therethrough.
In one embodiment, the bearing also includes being arranged at first exterior section and second outside portion / spacer ring.The spacer ring can be made up of elastomeric material.
In one embodiment, the external member includes the first exterior section and the second exterior section, wherein, it is described Second exterior section is screwed into first exterior section.
Also disclosed herein is a kind of bearing for being hinged tilting airplane wingtip articulated elements.The bearing includes external member, should External member has the interior zone defined by concave inside surface.The bearing also includes internals, and the internals has First interior section and the second interior section.First interior section has the first bottom and axially extending from first bottom Clutch shaft bearing part.Second interior section has the second bottom and from the axially extending second bearing portion in second bottom Point.The clutch shaft bearing part and the second bearing part are collectively forming outside the convex complementary with the concave inside surface shape Surface.The bearing also includes by the gap (such as variable-sized gap) between first interior section and the second interior section The preloading component for being formed.Lubricating bushings are provided between the concave inside surface and the convex external surface.Inside described first Simultaneously elasticity is outer partially towards mutual direction elastic compression for part and second interior section, by the external member and the inside Axial movement between component is limited to a default size.First interior section and second interior section are suitable to institute State bushing abrasion and outcurve, so as to by it is described axial movement be held in the default size.
Brief description of the drawings
Fig. 1 is the schematic perspective view that existing band is hinged tilting wing tip aircraft；
Fig. 2 is a kind of stereogram of implementation method of thrust bearing of the present invention；
Fig. 3 is the schematic top plan view of Fig. 2 thrust bearings；
Fig. 4 is the view in transverse section of 4-4 along the bearing of the preloading component of band in Fig. 2；
Fig. 5 is the amplification sectional view of the alternate embodiments of the part in 4-4 sections along Fig. 4；
Fig. 6 is the magnified partial view in Fig. 4 sections, wherein, the preloading component is in loading position；
Fig. 7 is the magnified partial view in Fig. 4 sections；
Fig. 8 is the sectional view suitable for bushing shown in Fig. 4 of the invention；
Fig. 9 is the sectional view of another implementation method suitable for bushing shown in Fig. 4 of the invention；
Figure 10 is the stereogram of another implementation method of thrust bearing of the present invention；
Figure 11 is the cross-sectional perspective view of 11-11 along thrust bearing shown in Figure 10；
Figure 12 is the magnified partial view of thrust bearing shown in Figure 11；
Figure 13 is the sectional view of another implementation method of thrust bearing shown in Figure 11；
Figure 14 is the enlarged drawing of 14-14 at Figure 13 details；And
Figure 15 is the stereogram of the elastic washer of the preloading component as thrust bearing shown in Figure 10 to Figure 14.
Specific embodiment
As shown in figure 1, the overall aircraft for being suitable to be used in combination with the disclosure of invention is represented with label 100.Aircraft 100 Wing 102 including being fixed to fuselage 101.Wing 102 also include radial type airplane wingtip 103,103 ' (call in the following text " wing tip 103, 103′”).Wing tip 103,103 ' is pivotally installed on wing 102 by articulated elements 104.Wherein, the element mark in Fig. 1 Numbers 103 and 103 ' are used to represent respectively that the minimum and maximums of wing tip 103,103 ' to stretch and tortuous state.Herein, " wing tip " One word refers generally to the attachment for being configured to change lift, and/or those skilled in the relevant art are generally regarded as wing tip Object.
Articulated elements 104 includes bearing 10, and it is, for example, the thrust bearing 10 similar with thrust bearing shown in Fig. 2.Such as Fig. 2 extremely Shown in Fig. 7, bearing 10 includes external member 12, internals 14, lubricating bushings 30 (such as self-lubricating bushing) and is arranged at Preloading component 50 in internals 14.External member 12 is interior including what is defined by concave inside surface 22 (best seen in Fig. 4) Portion region.A part for internals 14 is set in the interior zone of external member 12 and the longitudinal direction described in text (i.e. axial) axis A is rotated with one heart.
As shown in figure 4, internals 14 has bottom 14X and bearing portions 15, the bearing portions 15 is by clutch shaft bearing Part 14Y and second bearing part 14Z is defined, and this first, second bearing portions is axially extending from bottom 14X.Bearing portions 15 clutch shaft bearing part 14Y and second bearing part 14Z defines convex external surface 24, the convex external surface 24 and outside structure The shape of concave inside surface 22 of part 12 is complementary.Convex external surface 24 forms angle K with longitudinal axis A, so as to form overall V-shaped Cross section.
Lubricating bushings 30 be arranged at internals 14 convex external surface 24 and external member 12 concave inside surface 22 it Between.In one embodiment, lubricating bushings 30 are fixed to the concave inside surface 22 of external member 12, and with internals 14 Convex external surface 24 is slidably engaged.However, the invention is not restricted to this, lubricating bushings 30 can also be fixed to the convex of internals 14 Outer surface 24, and be slidably engaged with the concave inside surface 22 of external member 12.
As shown in figure 4, preload component 50 being located in bearing portions 15.In one embodiment, component 50 is preloaded by the Clearance G definition between one bearing portions 14Y and second bearing part 14Z.In a relaxed state, clearance G is by first axle bearing portion The predetermined interval definition divided between 14Y and second bearing part 14Z.
A part for bearing portions 15 is located in the interior zone, so that preloading component 50 by the He of external member 12 Axial movement between internals 14 is limited to default size.Component 50 is preloaded to be incited somebody to action by the direction of arrow C shown in Fig. 4 The mode that clutch shaft bearing part 14Y and second bearing part 14Z are mutually pressed towards each other is enabled (for example compress).By by clutch shaft bearing The mode that part 14Y and second bearing part 14Z are mutually pressed towards each other is compressed to preloading component 50 can be by internals 14 Interference fit between the concave inside surface 22 of convex external surface 24 and external member 12 is realized.That is, preloading component 50 Can be radially and/or axially outer inclined in the direction of arrow D, so as to promote clutch shaft bearing part 14Y and second bearing part 14Z mutual Engaged away from and with lubricating bushings 30.Preloading component 50 in internally positioned component 14 has applying outer peripheral preloading to its Lotus, so that the load against lubricating bushings 30 is generated, and it is thus achieved that any mill that may occur during to the life-span of bearing 10 Damage the compensation of (such as liner wear).In one embodiment, when preloading component 50 is compressed, clutch shaft bearing part 14Y And the clearance G between the 14Z of second bearing part reduces a default size.(trigger abrasion after the assembling of bearing 10 and using preceding Before) original state under, internals 14 relative to the axial movement of external member 12 be restricted to about zero it is default big It is small.
Preload component 50 and be set to liner wear radially and/or axially outcurve, by external member 12 and internal structure Axial movement between part 14 more preferably keeps, accurately keeps and/or is limited to the default size.That is, preloading Component 50 is set to compensate the default wear extent of lubricating bushings 30.Although the foregoing describing to external member 12 and inside The limitation that axial movement between component 14 is carried out, but it will be appreciated by those skilled in the art that it also impliedly represents preloading Component 50 can other motions be kept and/or are limited equally to radial motion etc..
As shown in figure 4, external member 12 includes the first exterior section 12A and the second exterior section 12B.First exterior section 12A and the second exterior section 12B are fixed to one another by suitable fasteners as herein described.For example, multiple bolts 16 are respectively protruding into In the multiple correspondence screw 17B of the second exterior section 12B, and it is screwed into the multiple correspondence spiral shell being formed on the first exterior section 12A In the 17A of hole.First exterior section 12A shown in Fig. 4 and the second exterior section 12B is overall symmetrically (such as forming mirror image).
Although the first exterior section 12A and the second exterior section 12B illustrates and is described as overall symmetrical, this hair Bright not limited to this, the first exterior section 12A and the second exterior section 12B can also have other configurations.For example, as shown in fig. 6, One exterior section 212A is more than the second exterior section 212B and with towards the second exterior section 212B axially extending blade 213. In addition, as shown in fig. 6, being provided with spacer ring 60 between the first exterior section 212A and the second exterior section 212B.Implement in one kind In mode, spacer ring 60 is made up of elastomeric material.
Fig. 4 is referred again to, internals 14 includes the first interior section 14A and the second interior section 14B.First inside portion 14A and the second interior section 14B is divided to be fixed to one another by suitable fasteners as herein described.For example, multiple bolts 18 are stretched respectively Enter in the multiple correspondence screw 19B of the second interior section 14B, and be screwed into the multiple correspondence being formed on the first interior section 14A In screw 19A.First interior section 14A shown in Fig. 4 and the second interior section 14B is overall symmetrically (such as forming mirror image). However, the invention is not restricted to this, the first interior section 14A and the second interior section 14B can have different shape and can not be mutual Symmetrically.
In one embodiment, as shown in figure 4, external member 12 also includes the peace radially extended from the external member 12 Dress flange 12M.In one embodiment, mounting flange 12M includes multiple holes, and each hole is through mounting flange 12M Through hole.In one embodiment, external member 12 has multiple through through hole 20.Mounting flange 12M can be fixed to and be hinged Part 104, wing tip 103 or bottom 102.As shown in figure 4, internals 12 has the interior zone 45 defined by inner surface 44. Inner surface 44 is set to accommodate the axle or bar (not shown) connected with articulated elements 104, wing tip 103 or bottom 102.
In one embodiment, as shown in figure 5, internals 114 is an integrated member, and external member 112 is wrapped Include the first exterior section 112A and the second exterior section 112B that similar suitable fasteners as shown in Fig. 4 interfix. In Fig. 5, the preloading component of internals 114 is by acting on the outward flange of internals 114 and making lubricating bushings 130 bear to compress The preload force definition of power.
As shown in figure 8, lubricating bushings 30 include a plurality of lubricant fiber 31 in support system.In a kind of implementation method In, the support system has a plurality of support fiber 33, and notes the resin 39 between support fiber 33 and lubricant fiber 31. In one embodiment, a plurality of lubricant fiber 31 is made up of polytetrafluoroethylene (PTFE) (PTFE) material, nylon and/or graphite. In one embodiment, a plurality of support fiber 33 (is write poly- sometimes by glass fibre, polyethylene terephthalate (ethylene glycol terephthalate), is commonly abbreviated as PET, PETE), polyester, cotton, meta-aromatic polyamide Material is (such as) and/or contraposition aromatic polyamide synthetic material is (such as) be made.In a kind of embodiment party In formula, the resin system include polyester resin, epoxy resin, phenolic resin, polyurethane resin, polyimide resin and/or Polyamide.In one embodiment, the support system includes the filler in compound resin system, the compound resin System includes polyester resin, epoxy resin, phenolic resin, polyurethane resin, polyimide resin and/or polyamide. In a kind of implementation method, described filler includes glass fibre, graphite, bronze, molybdenum bisuphide and/or carbon fiber.
As shown in figure 9, another implementation method of lubricating bushings is represented with label 130.Lubricating bushings 130 include the first fiber (such as fabric) layer 35, the second fiber (such as fabric) layer 32X and the 3rd fiber (such as fabric) layer 32Y.First fibrage 35 by moistening certainly The mixture of sliding fiber 32A and support fiber 32B is made.Second fibrage 32X and the 3rd fibrage 32Y is by support fiber 32B is made.In one embodiment, a plurality of self-lubricating fiber 32A is polytetrafluoroethylene (PTFE) (PTFE).In a kind of embodiment party In formula, a plurality of self-lubricating fiber 32A includes graphite fibre.In one embodiment, a plurality of support fiber 32B is Glass fibre, polyethylene terephthalateFiber, polyester fiber, cotton fiber, meta-aromatic polyamideFiber and/or contraposition aromatic polyamideFiber.In one embodiment, lubricious liner Set 130 includes the filler being placed in one, such as but not limited to glass fibre, graphite, bronze, molybdenum bisuphide and carbon fiber.One Plant in implementation method, lubricating bushings 130 are made up of PTFE matrix, and the filler including being placed in one.
Lubricating bushings 130 also include the first hypothallus (being made up of resin system) 34X, the second hypothallus (i.e. by resin System is made) 34Y and the 3rd hypothallus (being made up of resin system) 34Z.In one embodiment, the first hypothallus 34X, the second hypothallus 34Y and the 3rd hypothallus 34Z the resin system include polyester resin, epoxy resin, phenolic resin, Polyurethane resin, polyimide resin and/or polyamide.
First hypothallus 34X directions as shown in arrow F are pressed into the first fibrage 35, so that the first hypothallus 34X bags The first fibrage 35 is sealed, and the resin system of the first hypothallus 34X injects the first fibrage 35 and is in self-lubricating fiber 32A And support fiber 32B between and around.
First hypothallus 34X and the second hypothallus 34Y direction as shown in arrow F are pressed into the second fibrage 32X, so that First hypothallus 34X and the second hypothallus 34Y encapsulates the second fibrage 32X, and the first hypothallus 34X and the second hypothallus The resin system of 34Y injects the second fibrage 32X and between support fiber 32B and around.
Second hypothallus 34Y and the 3rd hypothallus the 34Z direction as shown in arrow F are pressed into the 3rd fibrage 32Y, so that Second hypothallus 34Y and the 3rd hypothallus 34Z encapsulates the 3rd fibrage 32X, and the second hypothallus 34Y and the 3rd hypothallus The resin system of 34Z injects the 3rd fibrage 32Y and between support fiber 32B and around.
In the another embodiment shown in Figure 10 to Figure 15, articulated elements 104 includes and bearing 10 shown in Fig. 2 to Fig. 7 Similar thrust bearing 310, therefore similar component uses the like reference numerals started with numeral 3 to represent.Thrust bearing 310 Including internals 314, the external member 312 around internals 314, and it is arranged at internals 314 and external member Lubricating bushings 330 (such as self-lubricating bushing) between 312.Thrust bearing 310 also includes being arranged at preloading in internals 314 Component 350.
External member 312 includes the interior zone defined by concave inside surface 322.A part for internals 314 sets Rotate concentric with longitudinal direction as herein described (i.e. axial) axis A is set in the interior zone of external member 312.
As shown in figure 12, internals 314 includes the first interior section 314A and the second interior section 314B, this two parts Mirror image each other.External member 312 includes the first exterior section 312A and the second exterior section 312B.First exterior section 312A is big In the second exterior section 312B, and with blade 313 vertically to the second exterior section 312B extensions thereon.Outside first Part 312A and the second exterior section 312B are bonded with each other by screw thread, and this is threadedly engaged also by the first interior section 314A and Two interior section 314B are fixed between two exterior section.
As shown in figure 12, external member 312 also includes the mounting flange 312M radially extended from the external member 312.Peace Dress flange 312M can be fixed to articulated elements 104, wing tip 103 or bottom 102.As is illustrated by figs. 11 and 12, the first internals There is 312A inner surface 344A, the second internals 312B to have inner surface 344B.Inner surface 344A and 344B definition are portalled 345, for accommodating the axle or bar (not shown) that are connected with articulated elements 104, wing tip 103 or bottom 102.
First interior section 314A has from inner surface 344A radially overhanging bottom 351A, the second interior section 314B tools Have from inner surface 344B radially overhanging bottom 351B.First interior section 314A has and inwardly stretched from bottom 351A axle and radially Overhanging cone bearing part 315A, the second interior section 314B to be had inwardly stretched from bottom 351B axle and radially overhanging taper Bearing portions 315B.Component 350 is preloaded to be arranged between clutch shaft bearing part 315A and second bearing part 315B and with it extremely Small part is engaged.
Cone bearing part 315A and 315B is spaced separation by clearance G 12, and is collectively forming the convex of internals 314 Shape outer surface 324, the convex external surface 324 is complementary with the shape of concave inside surface 322.Convex external surface 324 with parallel to longitudinal direction The angled K of the linear of axis A.
As shown in figure 12, the first interior section 314A has inwardly the second inside portion that is formed within and is open axially The first C-shaped chamber 352A of point 314B, the second interior section 314B have be formed within and be open it is axial inwardly in first The second C-shaped chamber 352B of portion part 314A.Preload component 350 be, for example, spring washer and be compressed in the first interior section 314A and Between the first and second C-shaped chamber 352A and 352B between second interior section 314B, so as to by the first interior section 314A and Second interior section 314B mutually axially extrapolates along direction shown in arrow V.
With reference to Figure 12, the blade 313 on the first exterior section 312A has the box thread being formed in its inner radial surface Region 313T.Second exterior section 312B has the male thread region 312T being formed on its radially-outer surface.Second outside portion 312B is divided to be screwed into the first exterior section 312A, so as to first exterior section 312A is fixed into the second exterior section 312B.The One exterior section 312A includes the shoulder 313E inwardly stretched from the footpath of blade 313.Second exterior section 312A includes abutting edge 312E, when the first exterior section 312A is screwed into the second exterior section 312B completely, abutting edge 312E abutment shoulders 313E, to prevent the axial movement between the rwo.
As shown in figure 11, the second exterior section 312B of external member 312 has the multiple holes being formed in its axial face 388, this pores is used to accommodate instrument (for example, open-end wrench, not shown), in order to installing and revolving the second exterior section 312B Enter the first exterior section 312A, and beneficial to follow-up disassembling section.In one embodiment, threaded portion 312T and 313T has There is coating thread locking fluid thereon, to prevent the second exterior section 312B to be not intended to release with the first exterior section 312A. In one embodiment, the first exterior section 312A and the second exterior section 312B is by the anti-rotation devices 399 such as pin or riveting (figure 12) it is fixed to one another.
As shown in figure 12, the first exterior section 312A has the radially inwardly conical surface, and the second exterior section 312B also has footpath To interior to the conical surface, this two conical surface is collectively forming the concave inside surface that the above-mentioned linear with parallel to longitudinal axis A is at an angle of K 322。
Lubrication is provided between the convex external surface 324 of internals 314 and the concave inside surface 322 of external member 312 Bushing 330.In one embodiment, lubricating bushings 330 are fixed to the concave inside surface 322 of external member 312, and with inside The convex external surface 324 of component 314 is slidably engaged.However, the invention is not restricted to this, lubricating bushings 330 can also be fixed to inside The convex external surface 324 of component 314, and be slidably engaged with the concave inside surface 322 of external member 312.In a kind of implementation method In, the construction of lubricating bushings 330 with Fig. 8 Suo Shi and describe lubricating bushings 30 it is identical.In another embodiment, lubricious liner Set 330 construction with Fig. 9 Suo Shi and description lubricating bushings 130 it is identical.
Preload component 350 and the axial movement between external member 312 and internals 314 be limited to a default size, For example limitation is to without axial movement.Clutch shaft bearing part 315A and second bearing part 315B are at least partially disposed at by table in spill In the interior zone defined in face 322, so that preloading component 350 is at least one of radial and axial direction Compression, and it is outer inclined at least one of radial and axial direction, so as to by between external member 312 and internals 314 Axial movement be limited to default size.Component 350 is preloaded to be set to the abrasion of lubricating bushings 330 in radial and axial At least one side be bent upwards, so as to by it is described axial movement be held in the default size.
Preload component 350 by the direction of arrow C shown in Figure 12 by the first interior section 314A and the second inside portion The mode for dividing 314B mutually to press towards each other is enabled (for example compress).By by the first interior section 314A and the second interior section 314B Mutually the mode of pressure is compressed and can be screwed into the first exterior section by by the second exterior section 312B to preloading component 350 towards each other The mode of 312A is realized.That is, the axis of orientation for preloading component 350 along arrow V is outwards inclined, so as to promote the first interior section 312A and the second interior section 312B are located remotely from each other and are engaged with lubricating bushings 330.The preloading component 350 of internals 314 Generate the load against lubricating bushings 330, and it is thus achieved that any abrasion that may occur during to the life-span of thrust bearing 310 The compensation of (such as liner wear).In one embodiment, when preloading component 350 is compressed, clearance G 12 reduces one and presets Size.Under original state after the assembling of thrust bearing 310 and using preceding (trigger abrasion before), internals 314 relative to The axial movement of external member 312 is restricted to about zero default size.
Preload component 350 and be set to the abrasion of lubricating bushings 330 axially and/or radially outcurve, by external member Axial movement between 312 and internals 314 more preferably keeps, accurately keeps and/or is limited to the default size.Can See, preload component 350 and be set to compensate the default wear extent of lubricating bushings 330.Although the foregoing describing to outside structure The limitation that axial movement between part 312 and internals 314 is carried out, but various equivalent modifications are it will be appreciated that it is gone back Impliedly represent that preload component 350 other can move and kept and/or limited equally to radial motion etc..
Thrust bearing 410 shown in Figure 13 and Figure 14 is similar to the thrust bearing 310 shown in Figure 10 to Figure 12.Therefore, phase Used with element and represented with the like reference numerals of digital 4 substitution primary 3.Between thrust bearing 310 and thrust bearing 410 Larger difference be, the first interior section 414A and the second interior section 414B mutually be mirror image.Conversely, the second inside portion There is axially extending leg 414L, leg 414L to extend to the axial end 469 of the first interior section 414A to divide 414B.Such as This, the first interior section 414A is placed on the radially-outer surface 414K of leg 414L.Preload component 450 and be also placed in leg 414L's On radially-outer surface 414K, and with the similar fashion described by thrust bearing 310 shown in reference picture 10 to Figure 12, preload component 450 are compressed between the first interior section 414A and the second interior section 414B.
As shown in figure 15, it is the bullet with multiple axially extending crest 350P and trough 350V to preload component 350,450 Spring packing ring.Component 350,450 is preloaded to be compressed on arrow C directions, so that initial preload lotus is generated, by the first interior section 312A, 412A and the second interior section 314A, 414B mutually extrapolate along the direction of arrow V.Component 350,450 is preloaded by elastic Material be made, such as but not limited to elastomeric material and spring steel.
There is disclosed herein one kind by the external member 12,312,412 and internals 14,314 of bearing 10,310,410, Axial movement between 414 is held in the method in pre-set limit.The method includes, there is provided external member 12,312,412 and It is internally provided with the internals 14,314,414 of preloading component 50,350,450.Lubricating bushings 30,330,430 are also provided.It is interior Portion's component 14,314,414 is at least partially arranged at external member 12, and in 312,412, and lubricating bushings 30,330,430 are arranged at Internals 14,314,414 and external member 12, between 312,412.Preload component 50,350,450 to be compressed so that lubrication The abrasion of bushing 30,330,430 can be compensated by the expansion of the preloading component 50,350,450, so as to by lubricating bushings Internals 14,314,414 and external member 12 before and after 30,330,430 abrasions, the axial movement between 312,412 are held in In pre-set limit.
Although being below shown and described to the present invention by reference to specific embodiment, art technology Personnel are it will be appreciated that without departing from the scope of the invention, can also make various changes and be replaced with equivalent Change its element.Additionally, in the case where essential scope of the present invention is not departed from, also particular case or material can be made by making modification Adapt to teachings of the present invention content.Therefore, the present invention be not intended to be restricted to it is described in detail above disclosed in specific implementation Mode, conversely, the present invention includes all implementation methods for falling within the scope of the appended claims.

Claims (10)

1. one kind is hinged wing bearing, it is characterised in that including：
External member, with the interior zone defined by concave inside surface；
Internals, with the first interior section and the second interior section,
First interior section has the first bottom and from the axially extending clutch shaft bearing part in first bottom,
Second interior section has the second bottom and from the axially extending second bearing part in second bottom, and
The clutch shaft bearing part and the second bearing part are collectively forming the convex complementary with the concave inside surface shape Outer surface；
Preload component, between the clutch shaft bearing part and the second bearing part and with the clutch shaft bearing part and At least a portion of the second bearing part is engaged；
Lubricating bushings, between the concave inside surface and the convex external surface；
At least a portion of the clutch shaft bearing part and the second bearing part is located in the interior zone so that described Preload component to be compressed inwardly at least one of radial and axial direction, so as at least one of radial and axial It is outer inclined on direction, the axial movement between the external member and the internals is limited to a default size；And
The preloading component is suitable to the abrasion of the bushing outcurve at least one of radial and axial direction, will The axial movement is held in the default size.
2. bearing as claimed in claim 1, it is characterised in that the external member includes the first exterior section for interfixing With the second exterior section.
3. bearing as claimed in claim 1, it is characterised in that first interior section and second interior section are mutual It is fixed.
4. bearing as claimed in claim 1, it is characterised in that the external member is formed with the mounting flange for radially extending.
5. bearing as claimed in claim 4, it is characterised in that the mounting flange includes multiple through holes therethrough.
6. bearing as claimed in claim 2, it is characterised in that also including being arranged at first exterior section and described second Spacer ring between exterior section.
7. bearing as claimed in claim 6, it is characterised in that the spacer ring includes elastomeric material.
8. bearing as claimed in claim 1, it is characterised in that the external member is included outside the first exterior section and second Part, second exterior section is screwed into first exterior section.
9. bearing as claimed in claim 1, it is characterised in that the preloading component includes ring spring.
10. one kind is hinged wing bearing, it is characterised in that including：
External member, with the interior zone defined by concave inside surface；
Internals, with the first interior section and the second interior section,
First interior section has the first bottom and from the axially extending clutch shaft bearing part in first bottom,
Second interior section has the second bottom and from the axially extending second bearing part in second bottom, and
The clutch shaft bearing part and the second bearing part are collectively forming the convex complementary with the concave inside surface shape Outer surface；
Preload component, including the gap between first interior section and second interior section；
Lubricating bushings, between the concave inside surface and the convex external surface；
Simultaneously elasticity is outer partially towards mutual direction elastic compression for first interior section and second interior section, will be described outer Axial movement between portion's component and the internals is limited to a default size；And
First interior section and second interior section are suitable to the outcurve with the abrasion of the bushing, by the axial direction Motion is held in the default size.
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EP3173639B1 (en) 2019-10-02
CN106812789B (en) 2018-10-26
US20170152889A1 (en) 2017-06-01
US9856910B2 (en) 2018-01-02

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